Scramjet propulsion

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Scramjet propulsion / edited by E.T. Curran and S.N.B. Murthy

資料種別:

図書

出版情報:

Virginia : American Institute of Aeronautics and Astronautics, c2000

形態:

xxvii, 1293 p. ; 24 cm

シリーズ名:

Progress in astronautics and aeronautics ; v. 189 <BA00087068>

著者名:

ISBN:

9781563473227 [1563473224]

書誌ID:

BA51581753

子書誌情報

フルテキスト

所蔵情報

他の版・巻

書誌詳細

言語:

英語

目次情報:

Preface

Introduction

International Efforts / I.：

Inlets, Combustors, and Fuels / II.：

Overall Systems / III.：

Future Developments / IV.：

Closing Comments / V.：

References

Scramjet Testing in the T3 and T4 Hypersonic Impulse Facilities / Chapter 1：

Nomenclature

History, Aims, and Developments

Facility and Instrumentation

Fuel-Injection Systems

Combustion/Mixing Processes

Simple Theoretical Combustor and Thrust Model

Experimental Results of Specific Impulse / VI.：

Effects of Atomic Oxygen and Nitric Oxide in the Freestream / VII.：

Different Fuels / VIII.：

Integrated Scramjet Measurements / IX.：

Skin-Friction Measurements / X.：

Discussion and Review / XI.：

Acknowledgments

Bibliography

Scramjet Developments in France / Chapter 2：

Historical Overview

Basic Research on Diffusion Flame Combustion (1962-1967)

ESOPE Program (1966-1973)

Studies on Shock-Induced Combustion

Prepha Program (1992-1997)

Perspectives

Scramjet Investigations Within the German Hypersonics Technology Program (1993-1996) / Chapter 3：

German Hypersonics Technology Program and Scramjet-Related Activities

Theoretical Investigations for Scramjet Intake Designs

Theoretical and Experimental Investigations of Scramjet Combustion at TsAGI and DLR Lampoldshausen

Freejet Wind-tunnel Testing of Scramjet Propulsion Systems at TsAGI

Considerations for Flight Testing Small-Scale Scramjet Modules Using the RADUGA-D2 Flying Testbed

Scramjet Engine Research at the National Aerospace Laboratory in Japan / Chapter 4：

Engine Model

Test Facility

Measurements

5 Test Results

Supplementary Studies for Engine Testing

Conclusions and Future Prospects

Scramjet Research and Development in Russia / Chapter 5：

Initial Stage of Scramjet Investigations (1957-1972)

Scramjet Investigations in 1972-1996

Short Remarks on Scramjet Inlet and Nozzle Developments

Conclusion

Three Problems in Supersonic Combustion / Appendix A：

Deceleration of Supersonic Flows in Smoothly Diverging-Area Rectangular Ducts / Appendix B：

Some Aspects of Scramjet-Vehicle Integration / Appendix C：

Leading-Edge Bluntness Effect on Performance of Hypersonic Two-Dimensional Air Intakes / Appendix D：

Scramjet Performance / Chapter 6：

Cycle Considerations

Flow Nonuniformity and Cycle Performance

Inlet

Sidewall Compression Concepts

Interactive Inlet Design

Inlet/Isolator Interactions

Combustor

Hypersonic Combustion Physics

Simulation Requirements

Experimental Simulation

Comparison of Combustion Data

Instrumentation/Measurement Requirements

Computational Simulation

Computational Methods

Combustor Performance Index--Thrust Potential

Nozzle

Engine/Vehicle System Integration

Forebody/Inlet

Nozzle/Afterbody

Concluding Remarks

Central Institute of Aviation Motors NASA MACH 6.5 Scramjet Flight Test

Experimental Apparatus and Test Conditions

Flight and Ground-Test Results

NASA'S Hyper-X Program

Flight-Test Vehicle Design and Fabrication

Flight-Test Plans

Hyper-X Technology

Scramjet Inlets / Chapter 7：

Definitions of Performance Parameters

Inlet Design Issues

Engine Cycle Calculations

Performance Measurement Techniques

Design and Performance of Scramjet Inlets

Summary and Recommendations for Future Investigations

Supersonic Flow Combustors / Chapter 8：

Phenomenological Considerations

Design Approach Implications

Fuel Injection Basics

High Mach Number Implications

Inlet One-Dimensional Continuity and Energy Flow Solution

Profile Flow Solution

Entropy Limit Concept

Combustor Thrust Potential Concept

Aerothermodynamics of the Dual-Mode Combustion System / Chapter 9：

H-K Diagram

Dual-Mode Combustion System

One-Dimensional Flow Analysis of the Isolator-Burner System

System Analysis of Isolator-Burner Interaction

Interpretation of Experimental Data

Closure

Basic Performance Assessment of Scram Combustors / Chapter 10：

Scram-Combustor Effectiveness

Computational Tool and Limitations

General Illustrative Studies

Specific Illustrative Studies

Scaling Performance and Geometry

Combustor-Based System Integration

Efficiency Relations

Heat Addition to a Supersonic Gas Flow

Constant Pressure Heat Addition in a Duct

Constant Mach Number Heat Addition in a Duct

Heat Addition in a Constant Area Duct

Heat Addition in a General Diverging Area Duct

Heat Addition Following a Shockwave

Efficiencies in Heat Addition

Hydrogen Combustion Scheme

Thermodynamic Properties

Equilibrium and Nonequilibrium Combustion

Three-Dimensional Nozzles--Design and Integration

Internal Flowpath

Integration with the Vehicle External Flow

Strutjet Rocket-Based Combined-Cycle Engine / Chapter 11：

Strutjet Engine

Strutjet Engine/Vehicle Integration

Available Hydrocarbon and Hydrogen Test Data and Planned Future Test Activities

Maturity of Required Strutjet Technologies

Summary and Conclusions

Liquid Hydrocarbon Fuels for Hypersonic Propulsion / Chapter 12：

Fuel Heat-Sink Requirements and the Role of Endothermic Fuels

Fuel System Challenges

Combustion Challenges

Summary

Addendum--Recent Work

Basic Elements of Chemical Kinetic Mechanisms / Appendix：

Thermochemical and Kinetic Databases

Construction and Validation of Comprehensive Combustion Models

Formal Routes to Sensitivity Analyses and Mechanism Reduction

Skeletal Models

Detonation-Wave Ramjets / Chapter 13：

Experimental Evidence of Standing Detonation Waves

Operating Envelope of Standing Detonation Waves

Fuel/Air Premixing Process

Performance Analysis

Scramjet/Airframe-Integrated Waverider

Problem of Hypersonic Flow Deceleration by Magnetic Field / Chapter 14：

Peculiarities of MHD Control

Review of Proposals to Use MHD Control

Contents of the Present Article

Relative Value of MHD Effects in Hypersonic Airflows

Electroconductivity of Air and Dimensionless MHD Parameters Behind a Normal Shock Wave in a Hypersonic Flow

Evaluation of Capabilities of Conductivity Increase in Pure Air

Equations of Magnetic Gas Dynamics at Small Magnetic Reynolds Numbers. Main Parameters. Methods of Numerical Analysis

Equations of Magnetic Gasdynamics and Main Dimensionless Parameters

Parameters Describing Irreversible Losses in MHD Flows

MHD Deceleration of a Hypersonic Flow in One-Dimensional Approach

Numerical Method for Solution of MHD Equation System

Boundary-Layer Separation Parameter in Magnetogasdynamics

Parameter of Boundary-Layer Separation in the Case of Nonconducting Wall

Parameter of Boundary-Layer Separation in the Case of Conducting Wall

Deceleration of a Supersonic Flow in a Circular Nonconducting Tube by an Axisymmetric Magnetic Field

Flow Deceleration in a Circular Tube by Magnetic Field of a Single-Current Loop

Flow Deceleration in a Circular Tube by Magnetic Field of a Solenoid

Deceleration of Two-Dimensional Supersonic Flow in Channels by Magnetic Field Perpendicular to a Flow Plane In Generator Regime

Formulation of a Problem

Quasi-One-Dimensional Approximation for Electrical Variables

Numerical Analysis of Laminar and Turbulent Flows

Conclusions

Rudiments and Methodology for Design and Analysis of Hypersonic Airbreathing Vehicles / Chapter 15：

Rudiments of Design

Coordinate System

Force Accounting System

Nominal SSTO Vehicle/Trajectory

Loads

Stability and Control

Representative Forces and Moments

Impact of Propulsion Lift on Aerodynamics

Engine/Airframe Integration Methodology

Engineering Methods

Higher-Order Numerical Methods

Vehicle Design Methodology

Aerodynamics/Aerothermodynamics

Structures/TPS Sizing

Vehicle Performance

Synthesis/Sizing

Design Automation/Optimization

Transatmospheric Launcher Sizing / Chapter 16：

Vehicle Sizing Approach

Propulsion Systems

Sizing Code

VDK Sizing Approach

SSTO Launcher Sizing

TSTO Launcher Sizing

Comparison Between SSTO and TSTO

Air Liquefaction and LOX Collection

Hypersonic Configuration Geometric Characteristics

Impact of Lower Speed Thrust Minus Drag

Scramjet Flowpath Integration / Chapter 17：

Background

Energy Analysis

Forebody

Force Accounting

Nozzle Component Losses

Integration Results

Summary and Recommendations

Dynamics of a Flight Vehicle

Brayton Cycle Scramjet

Aerothermodynamics of Scramjet Engine

Hypersonic Slender Body Theory Applied to Forebodies and Leading Edges

Scaling Drag and Heat Transfer / Appendix E：

Force Accounting Procedures / Appendix F：

Geometry and Mass of Integrated Vehicle / Appendix G：

Two-Wave Combustion Model for Optimal Supersonic Combustion Performance / Appendix H：

Base Pressure Estimate / Appendix I：

Nomenclature for Flow Path Component Specification

Preface

Introduction

International Efforts / I.：

Inlets, Combustors, and Fuels / II.：

Overall Systems / III.：

Future Developments / IV.：

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